FIELD: engine technology.
SUBSTANCE: system is designed to regulate fuel supply to the gas turbine engine. A hydraulic command is supplied to the inlet throttle-spool of the inter-throttle hydraulic flow chamber of the reserve control channel from a spring-loaded corrector spool, the inlet of which is connected to a constant pressure valve, and the spring cavity forms an inter-throttle hydraulic flow chamber, to the inlet throttle of which a hydraulic command is supplied from a pneumatic hydraulic converter.
EFFECT: implementation of the regulation system according to this scheme makes it possible to realize, with a change in flight altitude and speed, an optimal change in fuel consumption in the engine, corresponding to the needs of a certain aircraft engine or its modification.
1 cl, 1 dwg
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